公开(公告)号：US20150183514A1

公开(公告)日：2015-07-02

申请号：US14643857

申请日：2015-03-10

Applicant: DZYNE Technologies, Inc.

Inventor： MARK ALLAN PAGE ,  MATTHEW ROBERT MCCUE ,  ROBERT ANTHONY GODLASKY

IPC: B64C29/02 ,  B64C39/02 ,  B64C3/38 ,  B64C3/34 ,  B64C5/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165

Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

Abstract translation: 提供了一种用于固定翼飞行模式和转子飞行模式的飞机。 飞机可以包括机身，机翼和多个发动机。 机身可以包括还包括旋转支撑件的翼连接区域。 旋转部分可以包括旋转支撑件和机翼，其中多个发动机附接到旋转部分。 在转子飞行模式中，旋转部分可以围绕机身的纵向轴线旋转，为类似于直升机的转子的飞机提供升降机。 在固定翼飞行模式中，旋转部分不围绕机身的纵向轴线旋转，为类似于常规飞机的飞机提供升降机。 在转子飞行模式下为转子提供动力的相同发动机也为固定翼飞行模式下的飞机提供动力。

公开(公告)号：US20150028155A1

公开(公告)日：2015-01-29

申请号：US14378633

申请日：2013-02-13

Applicant: Johannes Reiter

Inventor： Johannes Reiter

IPC: B64C27/00 ,  B64C3/38 ,  B64C29/00

CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C3/385 ,  B64C27/00 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0075 ,  B64C29/02 ,  B64C37/00 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The present invention relates to a device for generating aerodynamic lift and in particular an aircraft (100) for vertical take-off and landing. A wing arrangement (110) comprises at least one propulsion unit (111), wherein the propulsion unit (111) comprises a rotating mass which is rotatable around a rotary axis (117). The wing arrangement (110) is mounted to a fuselage (101) such that the wing arrangement (110) is tiltable around a longitudinal wing axis (112) of the wing arrangement (110) and such that the wing arrangement (110) is rotatable with respect to the fuselage (101) around a further rotary axis that differs to the longitudinal wing axis (112). An adjusting mechanism adjusts a tilting angle of the wing arrangement (110) around the longitudinal wing axis (112) under influence of a precession force (Fp) which forces the wing arrangement (110) to tilt around the longitudinal wing axis (112).

Abstract translation: 本发明涉及一种用于产生空气动力升降装置，特别涉及用于垂直起飞和着陆的飞机（100）。 机翼装置（110）包括至少一个推进单元（111），其中推进单元（111）包括围绕旋转轴线（117）旋转的旋转块。 机翼装置（110）被安装到机身（101），使得机翼装置（110）围绕机翼装置（110）的纵向翼轴线（112）可倾斜，并且使得机翼装置（110）可旋转 相对于与纵向翼轴（112）不同的另一旋转轴线的机身（101）。 调节机构在促使机翼装置（110）围绕纵向机翼轴线（112）倾斜的进动力（Fp）的影响下调节机翼装置（110）围绕纵向翼轴线（112）的倾斜角度。

公开(公告)号：US08561937B2

公开(公告)日：2013-10-22

申请号：US12906096

申请日：2010-10-17

Applicant: Hosein Goodarzi

Inventor： Hosein Goodarzi

IPC: B64C27/00 ,  B64C29/00

CPC classification number: B64C39/024 ,  B64C39/064 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146

Abstract: The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servo motors and each of the plurality of the servo motors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servo motors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft.

Abstract translation: 本发明的各种实施例提供一种无人驾驶飞行器，其包括半球体，无刷电，螺旋桨，多个翼尖装置，多个伺服马达，多个伺服马达中的每一个连接到 多个翼尖装置，多个碳棒，以及壳体。 无刷式电动机为垂直起降提供提升力（VTOL），并且多个翼尖装置分为三种类型的翼尖装置，三种类型的翼尖装置由相应的伺服机构 用于控制偏航，俯仰和滚动运动的电机，从而稳定和控制飞行器的运动。

公开(公告)号：US08473125B2

公开(公告)日：2013-06-25

申请号：US13410229

申请日：2012-03-01

Applicant: Michael Rischmuller ,  Frederic D'haeyer

Inventor： Michael Rischmuller ,  Frederic D'haeyer

IPC: G06F13/00

CPC classification number: A63H27/12 ,  A63H30/04 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2203/00 ,  G05D1/0202 ,  G08C17/02 ,  G08C2201/93

Abstract: The respective motors of the drone (10) can be controlled to rotate at different speeds in order to pilot the drone both in attitude and speed. A remote control appliance produces a command to turn along a curvilinear path, this command comprising a left or right turning direction parameter and a parameter that defines the radius of curvature of the turn. The drone receives said command and acquires instantaneous measurements of linear velocity components, of angles of inclination, and of angular speeds of the drone. On the basis of the received command and the acquired measurements, setpoint values are generated for a control loop for controlling motors of the drone, these setpoint values controlling horizontal linear speed and inclination of the drone relative to a frame of reference associated with the ground so as to cause the drone to follow curvilinear path (C) at predetermined tangential speed (u).

Abstract translation: 无人机（10）的各个电机可以被控制为以不同的速度旋转，以便以姿态和速度引导无人机。 远程控制装置产生沿着曲线路径转动的命令，该命令包括左转或右转转方向参数和限定转弯曲率半径的参数。 无人机接收到所述命令，并获得无人机的线速度分量，倾角和角速度的瞬时测量值。 根据接收到的命令和采集的测量结果，产生用于控制无人机的电动机的控制回路的设定值，这些设定值控制无人机相对于与地面相关的参考系的水平线速度和倾角，因此 以使无人机以预定切向速度（u）跟随曲线路径（C）。

公开(公告)号：US08337156B2

公开(公告)日：2012-12-25

申请号：US12824514

申请日：2010-06-28

Applicant: Dmitry Sergeevich Khmel

Inventor： Dmitry Sergeevich Khmel

IPC: B64C11/30

CPC classification number: B64C11/306 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/165

Abstract: The invention relates to aeronautical engineering, in particular to methods of flight due to creating of forces on air propellers, namely using thrust vectoring of direction and amount of force created by air propellers of opposite rotation with the axis, mainly in the direction of flight, in the expanded range of speeds, from 50 m/s to high near-sonic speed of flight. The invention may be applied for horizontal flight and maneuvering in flight on vertical take-off aircrafts using rotation of main rotors from the vertical stand of rotor axes during the take-off to almost horizontal position of rotor axes in horizontal flight, thus both the rotation of rotors and the change of position of an aircraft together with its rotors may be applied, and it may be also used in the horizontal take-off aircrafts with almost horizontal position of axes during the horizontal flight, including the planes with airscrew propellers.

Abstract translation: 本发明涉及航空工程，特别涉及由于在空气螺旋桨上产生力而引起的飞行方法，即使用主要在飞行方向上与轴线相反旋转的空气推进器产生的方向和力的量的推力矢量， 在扩展的速度范围内，从50米/秒到高近似声速的飞行。 本发明可以应用于垂直起飞飞机中的水平飞行和机动飞行，其在起飞期间从转子轴的垂直支架转动到水平飞行中的转子轴线的几乎水平位置，从而旋转 可以应用转子和飞机与其转子的位置的变化，并且还可以在水平飞行中具有几乎水平的轴线位置的水平起飞飞机中使用，包括具有螺旋桨螺旋桨的平面。

公开(公告)号：US20120286102A1

公开(公告)日：2012-11-15

申请号：US13433276

申请日：2012-03-28

Applicant: Pranay Sinha ,  Jeffrey Kyle Gibboney ,  JoeBen Bevirt ,  Piotr Esden-Tempski ,  Christopher Allen Forrette ,  Gregory Mainland Horn

Inventor： Pranay Sinha ,  Jeffrey Kyle Gibboney ,  JoeBen Bevirt ,  Piotr Esden-Tempski ,  Christopher Allen Forrette ,  Gregory Mainland Horn

IPC: B64C13/20 ,  B64C27/26

CPC classification number: B64C29/02 ,  B64C15/00 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/02 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/165

Abstract: A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines. A tailless airplane which uses a control system that takes inputs for a traditional tailed airplane and translates those inputs to provide control utilizing non-traditional control methods.

Abstract translation: 一种适用于垂直起飞和着陆的载人/无人机，使用相同的发动机起飞和着陆以及向前飞行。 一种飞行器，其适于在垂直方向上与翼起飞，而不是水平飞行姿态，以垂直姿态起飞，然后转变到水平飞行路径。 一种飞行器，其在起飞和着陆期间通过交替发动机的推力来控制车辆的姿态，发动机的推力在起飞期间相对于水平在至少两个维度上分离，并且还可以通过使用 发动机差动推力。 一种无尾飞机，它使用控制系统，为传统的尾翼飞机提供输入，并转换这些输入，以提供使用非传统控制方法的控制。

公开(公告)号：US20120248259A1

公开(公告)日：2012-10-04

申请号：US13429156

申请日：2012-03-23

Applicant: Mark Allan Page ,  Matthew Robert McCue ,  Robert Anthony Godlasky

Inventor： Mark Allan Page ,  Matthew Robert McCue ,  Robert Anthony Godlasky

IPC: B64C27/24

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165

Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

Abstract translation: 提供了一种用于固定翼飞行模式和转子飞行模式的飞机。 飞机可以包括机身，机翼和多个发动机。 机身可以包括还包括旋转支撑件的翼连接区域。 旋转部分可以包括旋转支撑件和机翼，其中多个发动机附接到旋转部分。 在转子飞行模式中，旋转部分可以围绕机身的纵向轴线旋转，为类似于直升机的转子的飞机提供升降机。 在固定翼飞行模式中，旋转部分不围绕机身的纵向轴线旋转，为类似于常规飞机的飞机提供升降机。 在转子飞行模式下为转子提供动力的相同发动机也为固定翼飞行模式下的飞机提供动力。

公开(公告)号：US08256704B2

公开(公告)日：2012-09-04

申请号：US11838731

申请日：2007-08-14

Applicant: Gert Lundgren

Inventor： Gert Lundgren

IPC: B64C27/22

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/165

Abstract: A vertical/short take-off and landing aircraft with a single proprotor assembly that has a pair of inline counter-rotating rotors. Two inline counter-rotating engines are directly connected to the rotors. One engine is shut down in horizontal flight to improve efficiency. Gimbal mounting the proprotor assembly permits thrust to be directed forward to back and left to right to control pitch and roll when hovering. Varying the relative engine speeds controls yaw. The aircraft is adaptable as an unmanned vehicle.

Abstract translation: 具有单个推进器组件的垂直/短距起飞和着陆飞机，其具有一对在线的反向旋转的转子。 两个直列反向旋转发动机直接连接到转子上。 一个引擎在水平飞行中关闭以提高效率。 安装推进器组件的万向节允许推动力向前指向前向左并向左转，以便在悬停时控制俯仰和滚动。 改变相对发动机转速来控制偏航。 该飞机适用于无人驾驶的车辆。

公开(公告)号：US08141823B2

公开(公告)日：2012-03-27

申请号：US12949410

申请日：2010-11-18

Applicant: David C. Hursig ,  Steven D. Martinez

Inventor： David C. Hursig ,  Steven D. Martinez

IPC: G05D1/08

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162 ,  B64D45/04 ,  G05D1/0653 ,  G05D1/0858

Abstract: Takeoff and landing modes are added to a flight control system of a Vertical Take-Off and Landing (VTOL) Unmanned Air Vehicle (UAV). The takeoff and landing modes use data available to the flight control system and the VTOL UAV's existing control surfaces and throttle control. As a result, the VTOL UAV can takeoff from and land on inclined surfaces without the use of landing gear mechanisms designed to level the UAV on the inclined surfaces.

Abstract translation: 起飞和着陆（VTOL）无人机（UAV）的飞行控制系统增加起飞和着陆模式。 起飞和着陆模式使用可用于飞行控制系统和VTOL无人机现有控制面和节气门控制的数据。 因此，VTOL无人机可以在倾斜的表面上起飞和着陆，而不需要使用设计成在倾斜表面上对无人机进行平坦化的起落架机构。

公开(公告)号：US20110233329A1

公开(公告)日：2011-09-29

申请号：US13037436

申请日：2011-03-01

Applicant: Brian Theodore McGeer ,  Robert Joseph Heavey, III ,  Damon Lucas McMillan ,  John William Stafford

Inventor： Brian Theodore McGeer ,  Robert Joseph Heavey, III ,  Damon Lucas McMillan ,  John William Stafford

IPC: B64F1/02 ,  B64D37/16 ,  B64D37/20

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/182 ,  B64D37/00 ,  B64F5/00

Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or at a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a tether, and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured by a hook or other end effector. The tether length is then adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with simple and economical apparatus. It can be used with low risk of damage, and requires only moderate accuracy in manual or automatic flight control.

Abstract translation: 可以使用适合在小型船舶上使用的设备或具有类似有限空间或不规则运动的基座自动检索，维修和启动能够推力飞行的飞机。 为了检索，飞机坠落系绳，并以相对较低的速度牵引系绳与水平导轨接触。 将系绳拉过引导件，直到引导件被钩或其他端部执行器捕获。 然后根据需要调整系绳长度，并且飞机在引导件上摆动以悬在倒立的位置。 沿着导轨翻转系绳，然后将飞机带到对接车厢，飞机停在其中，以便维修。 为了发射，托架正直摆动，末端执行器从引导件释放，飞机起飞进入自由飞行。 因此，可以使用简单经济的装置自动完成全面的地面处理循环。 它可以使用低损害风险，并且在手动或自动飞行控制中只需要适度的准确性。